Patent application number | Description | Published |
20080209911 | Combination engines for aircraft - An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. | 09-04-2008 |
20080277533 | Aircraft combination engines inlet airflow control system - A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake. | 11-13-2008 |
20090007882 | Compound cycle rotary engine - A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption. | 01-08-2009 |
20090065652 | Aircraft combination engines exhaust thrust recovery - A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof to the air intake of an internal combustion engine provided as an intermittent combustion engine. The air intake and an exhaust outlet are each coupled to combustion chambers therein and a rotatable output shaft is also coupled to those combustion chambers for generating force. The exhaust outlet has an exhaust transfer duct extending therefrom so as to have the intermittent combustion engine be capable to provide exhaust therefrom in that exhaust transfer duct at one end thereof, and the exhaust transfer duct being connected at an opposite end thereof to the exhaust manifold to be capable of transferring intermittent combustion engine exhaust thereto. | 03-12-2009 |
20100011781 | HEAT EXCHANGER ASSEMBLY FOR AN AIRCRAFT CONTROL - A heat exchanger assembly for an aircraft control has an aircraft control for controlling an operation of an aircraft. The aircraft control is in thermal communication with a first fluid. A first thermoelectric device is configured to transfer heat between the first fluid and the second fluid against a temperature gradient of the first fluid and the second fluid. A temperature sensor is provided for sensing a temperature of the first fluid. A temperature control is also configured to control the first thermoelectric device based on an input from the temperature sensor. | 01-21-2010 |
20100170262 | AIRCRAFT POWER AND THERMAL MANAGEMENT SYSTEM WITH ELECTRIC CO-GENERATION - A power and thermal management system includes an integrated power package which receives bleed air, communicates conditioned air to an environmental control air distribution system and selectively communicates electrical power with an electrical distribution system. | 07-08-2010 |
20100236216 | TURBOFAN ENGINE WITH VARIABLE AREA FAN NOZZLE AND LOW SPOOL GENERATOR FOR EMERGENCY POWER GENERATION AND METHOD FOR PROVIDING EMERGENCY POWER - A turbofan engine ( | 09-23-2010 |
20100313591 | ADAPTIVE HEAT SINK FOR AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM - An avionics cooling system includes a first heat exchange system, a second heat exchange system and a vapor cycle system. The second heat exchange system has a heat sink capacity that is generally out of phase with a heat sink capacity of the first heat exchange system. The vapor cycle includes a fluid loop in communication with the first and second heat exchange systems and the fluid loop transfers heat to the first and second heat exchange systems. A method for cooling aircraft components includes selectively directing a fluid having an elevated temperature in a fluid loop of a vapor cycle system to a first heat exchanger to transfer heat from the fluid to a fuel based on a heat sink capacity of the fuel, selectively directing the fluid to a second heat exchanger to transfer heat from the fluid to air based on a heat sink capacity of the air, and cooling aircraft components with the fluid. | 12-16-2010 |
20150060023 | FIN-DIFFUSER HEAT SINK WITH HIGH CONDUCTIVITY HEAT SPREADER - A method and apparatus for cooling a heat source is disclosed. The apparatus includes a fin-diffuser including a blower integrated with fins of a diffuser. A heat spreader is coupled to the fin-diffuser. The heat spreader is configured to spread heat from a location proximate the blower to location of the fins. The apparatus spreads heat from a heat source proximate a blower of the fin-diffuser to a location away from the blower to cool the heat source. | 03-05-2015 |